Quick disconnect mounting



Jan. 11, 1955 TROEGER E 2,699,343

QUICK DISCONNECT MOUNTING Filed Dec. 20, 1950 2 Sheets-Sheet 1 INVENTORJ HENRY TROEGER RAYMOND D.PALFREYMAN v 11, 1955 H. TROEGER ETAL 2,699,343

QUICK DISCONNECT MQUNTING Filed Dec. 20, 1950 2 Sheets-Sheet 2 FIG. 2

JNVENTORS HENRY TROEGER RAYMOND D. PALFREYMAN United States Patent Ofifice QUICK DISCONNECT MOUNTING Henry Troeger, Ramsey, and Raymond D. Palfreyman,

Clifton, N. 1., assignors to Bendix Aviation Corporation, Teterboro, N. J., a corporation of Delaware Application December 20, 1950, Serial No. 201,764 1 Claim. (Cl. 285-129) The present invention relates to quick detachable means, such as mountings for accessories, and particularly to quick detachable means for mounting aircraft engine accessories.

effective quick detachable mount has preproblems. One of the outstanding probto its own resiliency maintains a clamping action at all times.

obiect of the invention is to provide improved quic Another ob ect of the invention is to provide a clamp ring for a quick detachable unit that is primarily stressed to maintain a clamping action.

Another obiect of the invention is to provide means for quickly attaching an accessory to an engine. bove and other obiects and 5 comprises an engine ada tor member ada tor member 7 and a clamp ring 8.

The member 6 has a circumferential flange 9 adapted to be secured by studs housing 15. The flanges 13 and 14 are provided with chamfers or bevel margins 18 and 19 at the axially remote sides thereof.

e clamping ring 8, see Figure 2, has an inwardly opening channel section 20 and is split at the periphery 21 to permit its expansion to a larger diameter. Lugs 2,699,343 Patented Jan. 11, 1955 23 and 24 are provided at the ends formed by the split 21. A screw 25 is provided for expanding the ring 8. One

a collar 27 tangential pin 27 fitting a screw 25. The ring inner edge to render the hannel 20 of the ring has sloping sides adapted with the chamfers 18 and 19 to bias the flanges form a seal therebetween.

In order to relieve the ring 8 of torque, pins 31 secured o the member 14 and adapted to be positioned in a hole 32 in the member 13 are provided. The number of pins 31 and mating holes 32 required will depend upon the type of accessory to be mounted.

In operation, the

ring 8 is expanded sufficiently to permit it being slipped over the flange 13 and rested on the member 6. The accessory 16 is then inserted in the hole 11 of with an engine member (not 13 and 14 together. The from turning in the mount due to torque.

due to its own resiliency tends to maintain the clamping To remove the accessory 16, the screw 25 is turned in a direction to spread the ring 8 to permit it to be slipped over the flanges 13 and 14 and onto the member 6 behind the fiange 13. The accessory 16 is then free to be removed.

Although only one embodiment of the invention has been illustrated and described, various changes in the at is claimed:

A clamping device useful in aircraft for clamping a driven accessory to the driving engine, comprising an open ended hoop spring strip, rectangular in cross section flat bottomed engageable with threaded means at the free ends of the hoop for spreading upon vibratlon of the engine, the hoop having its normal diametrical dimensions smaller (References on following page) 3 4 References Cited in the file of this patent ggggfli glsen ..l Ngali. 116, 1913 ,7 ustereta uy 1,194 UNITED STATES PATENTS 2,416,852 Schaatf Mar. 4, 1947 1,093,868 Leighty Apr. 21, 1914 2,439,161 Du Bois Apr. 6, 1948 LSiSg gastrfian hgay Pig, 5 2,580,396 Bluth Jan. 1, 1952 1, 8 1 utc inson ct. 1,997,385 Lodenkemper Apr. 9, 1935 FOREIGN PATENTS 2,080,988 Schulz May 18, 1937 199,010 Germany June 5, 1908 2,226,396 Wackmann Dec. 24, 1940 

